Q1) Air at mach number 2 over a wedge and generation of an oblique shock wave 40° . determine : 1. Static pressure and temperature downstream the shock. 2. The mach number of the flow downstream the shock. , pressure 0.5* 10 N/m² and a temperature of 0 °C , 3. The wedge angle. ********* ********* ******** ***********************

Consider steady, isentropic flow of air through a duct with varying area. At section 1, p1 = 15 kPa (abs), T = 10°C, Vị = 592 m/s, A1 = 0.25 m². At a downstream section 2, T2 = 137°C, Maz = 0.75. Determine: a. Mach number, Mai b. sketch geometry of the duct c. mass flow rate [kg/s] d. pressure, P2 [kPa] e. cross-sectional area, A2 [m2]

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Q2: The large compressed-air tank shown in the figure bellow exhausts from a nozzle at an exit velocity of V235 m/s. Assuming isentropic flow, compute: a) the exit Mach number. b) the pressure in the tank. (take; k = 1.396, C, = 917 J/Kg.k and R = 260 J/Kg.k) air at 30 C tank conditions Pan= 101 LPa

are 3000 ft/s and 500°R, respectively Calculate the Mach number M and the characteristic Mach number M* at this point 3.4. Consider a normal shock wave in air The upstream conditions are given by M = 3; P1 M2, u2, Po,, and T %3! = 1 atm, and p, = 1 23 kg/m Calculate the downstream values of P2, 02 35 Consider a Pitot static tube mounted on the pose of an experımental airplane A

1. The flow is considered compressible when the value of Mach number is.... (A) greater than unity (B) greater or equal to 0.3 (C) greater than 0.5 (D) less than 0.3 2. In c-d nozzle, when dA/dV is positive, then the flow is.... (A) subsonic (B) sonic (C) supersonic (D) incompressible 3. Along the adiabatic duct, the...... remains constant. (A) stagnation pressure (B) static pressure (C) static temperature (D) stagnation temperature 4. Across the normal shock wave, the gas velocity ...... (A) decreases↓ (B) increases ↑ (C) remains constant (D) varies randomly v2 (C) 2Cp (D) PV² 5. The dynamic temperature can be calculated from..... (A): M² 2Cp (B) -M² B 6. A supersonic flow with 38° oblique shock angle passes over a concave corner of angle 0=20°. Then, the free stream Mach number M₁ is.... (A) 2 (B) 5 7. Across the expansion waves, the ..... remains constant. (A) Mach number (B) stagnation pressure (C) 3 (C) gas velocity (D) 4 (D) temperature. (D) Pe=0 8. The maximal thrust of the…

3.4. Consider a normal shock wave in air The upstream conditions are given by M1 = 3; 1 23 kg/m' Calculate the downstream values of p2, T,, 1 atm, and p1 M2, u2, Po,, and T, P1 P24 02 Dis

3. The NASA X-43 flies at a Mach number of 9.4 at an altitude of 30,000 m, where thepressure is 1171.8 Pa and the temperature is 226 K. If a supersonic wind tunnel isdesigned to reproduce these conditions, calculate the following:(a) The velocity (m/s), total/stagnation temperature (K), and total/stagnation pres-sure (kPa) in the test section.(b) The velocity (m/s), total temperature (K), and total pressure (kPa) behind thenormal shock formed in front of a blunt surface in the test section.(c) The change in entropy across this normal shock.

An airplane fl ies at 555 mi/h. At what altitude in the standardatmosphere will the airplane’s Mach number beexactly 0.8?

derive an expression for the mass flowrate of air for a C-D nozzle arrangement operating in choked flow conditions. Hint: start with the fact that: mmax = p* A*V * show all your steps. upload your answer here.